CN103587707A - Power supply system of electronic flight instruments - Google Patents
Power supply system of electronic flight instruments Download PDFInfo
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- CN103587707A CN103587707A CN201310577406.1A CN201310577406A CN103587707A CN 103587707 A CN103587707 A CN 103587707A CN 201310577406 A CN201310577406 A CN 201310577406A CN 103587707 A CN103587707 A CN 103587707A
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Abstract
The invention provides a power supply system of electronic flight instruments. The power supply system can solve the problem of black screens and can not increase operation burden of a pilot. The system comprises an electronic gesture guide indicator arranged on a plane direct current breaker plate, an electronic horizontal position indicator, a display processor, an emergency bus bar and a power conversion relay. The emergency bus bar is used for providing stable power supply for an electronic flight instrument system. Power supply needed by the electronic flight instrument system is displayed and supplied automatically. Obsession, brought by the operation of a power switch of a display, on the pilot is removed.
Description
Technical field
The invention belongs to airplane synthetic avionics technical field, particularly a kind of Electronic Flight Instrument electric power system.
Background technology
Electronic type flight instrument system (EFIS) provides the demonstration of the information such as flying quality and navigation data for left and right driving, it receives from the output signal that receives heading and attitude system, air data system, autopilot, omnidirectional range/instrument landing/marker beacon system, macrometer, automatic direction finder, navigationsystem, radio altimeter and weather radar system on aircraft, for left and right driving provides corresponding demonstration information.And for showing meteorological radar, guidance station/way point, flight-control mode, relatively warning, Airspeed Tendency, checklist and diagnostic message.To autopilot, provide Pre-select Heading and main channel etc. for information about simultaneously.
On aircraft, by being arranged on the circuit breaker of EADI, EHSI, DPU, DCP major alarm on electronic type attitude director indicator (EADI) on left DC circuit breaker plate, electron type level notch indicator (EHSI), display processor (DPU), display control board (DCP) major alarm and right DC circuit breaker plate, to the armamentarium of EFIS system, power.The equipment of directly being powered by circuit breaker has left and right EADI; Left and right EHSI and EFD fan; Left and right DPU and DPU fan; Left and right DCP; Left and right II class approach light; Left and right major alarm lamp/reset button.After starting energising, equipment and fan thereof are worked simultaneously, the reduction of service life to prevent equipment excess temperature.Between two DPU by serial digital bus, this side joint is received from aircraft with the communication of side apparatus to opposite side, standby driver output is also sent to the standby driving input channel of opposite side DPU simultaneously.This kind of power supply mode is comparatively simple, but the problem existing is very obvious, when ground and machine power source conversion (engine starting), can cause Electronic Flight Instrument telltale to occur moment blank screen phenomenon; And when aircraft is under emergency service state, EFIS quits work, and will cause the loss of crucial navigation information.
The design of former electric power system exists above problem mainly to come from the airplane design initial stage, considers the loading level of storage battery, for guaranteeing the flying power of storage battery 30min under emergency rating, EFIS is directly connected to normal bus-bar.For head it off has proposed a scheme, be, increase Electronic Flight Instrument display power supply switch, after engine starting is stable, connect Electronic Flight Instrument display power supply switch.But this kind of power supply plan increased extra operation burden to aviator, and when this display power supply switch failure, flying instruments will thoroughly quit work, and not consider margin of safety problem.
By continuous test and improvement, design a kind of can solve engine starting time Bus Voltage moment reduce, Electronic Flight Instrument telltale moment blank screen phenomenon, does not increase again aviator's operation burden, does not subdue a kind of Electronic Flight Instrument electric power system of any function of flight instrument system.This system has finally been passed through seaworthiness application, and is verified and solved problem and the shortcoming that former electric power system exists by ground experiment.
Summary of the invention
The object of the present invention is to provide a kind ofly can solve blank screen phenomenon, do not increased again the Electronic Flight Instrument electric power system of aviator's operation burden.
A kind of Electronic Flight Instrument electric power system, this system comprises the left electronic type attitude director indicator (EADI) being arranged on the left DC circuit breaker plate of aircraft, left electron type level notch indicator (EHSI), left display processor (DPU), left emergent bus-bar and be arranged on the right electronic type attitude director indicator (EADI) on the right DC circuit breaker plate of aircraft, right electron type level notch indicator (EHSI), right display processor (DPU), power transfer relay, right emergent bus-bar, mounting bracket, the upper left electronic type attitude director indicator of left DC circuit breaker (EADI), left electron type level notch indicator (EHSI), the power supply of left display processor (DPU) is connected directly to left emergent bus-bar, the power supply of the right electronic type attitude director indicator (EADI) on right DC circuit breaker, right electron type level notch indicator (EHSI), right display processor (DPU) is connected to right emergent bus-bar by power transfer relay, power transfer relay is comprised of two relays of doing Anti-misplug design, and the excitatory end of power transfer relay is connected with the normal bus-bar of major alarm reset circuit breaker in flight instrument system, power transfer relay is connected to avionics system electronic equipment rack by mounting bracket.
Beneficial effect of the present invention is to provide stable power supply by emergent bus-bar for electronic type flight instrument system, and actv. has solved " blank screen " problem; Improved the margin of safety that the crucial navigation information of driving compartment shows,, under emergency service state, flight instrument system will have a set of display system continuous firing, guarantee that crucial flying quality can not lose.Switching relay is comprised of two relays of doing Anti-misplug design, accomplishes redundancy setting, and when wherein any relay lost efficacy, another can continuous firing, can not cause right side flying quality to disappear; By the excitatory normal bus-bar that is connected to major alarm reset circuit breaker in flight instrument system of relay; Do not affect on the one hand the conversion operations of display control board, do not increase on the other hand extra circuit breaker.Relay is connected to electronic equipment rack by mounting bracket.Be easy to the change of supply line, be easy to ground maintenance simultaneously.
Native system is owing to automatically providing EFIS to show required power supply, thereby eliminated the puzzlement that to display power supply switching manipulation brings aviator, alleviated aviator's operation bidirectional burden, and actv. has solved the problem that user proposes.Below in conjunction with specific embodiment, this invention is described in further detail.
Accompanying drawing explanation
Fig. 1 primary electron flying instruments power supply left-sided system block diagram
Fig. 2 primary electron flying instruments power supply right-sided system block diagram
Electronic Flight Instrument power supply left-sided system block diagram after Fig. 3 optimizes
Electronic Flight Instrument power supply right-sided system block diagram after Fig. 4 optimizes
Specific embodiment
By Fig. 1, Fig. 2, can find out that two cover flying instrumentss are connected directly to normal direct current (DC), and will cause the generation of blank screen phenomenon during in electric current instantaneous variation when direct current (DC).
And Fig. 3, Fig. 4 provide the Electronic Flight Instrument electric power system after a kind of optimize, and this kind of prioritization scheme be verified at aircraft, and actv. has solved fault and the defect that former electric power system is brought.This Electronic Flight Instrument electric power system, comprises left electronic type attitude director indicator (hereinafter to be referred as EADI), left electron type level notch indicator (hereinafter to be referred as EHSI), left display processor (hereinafter to be referred as DPU), the left emergent bus-bar being arranged on the left DC circuit breaker plate of aircraft and is arranged on right EADI, the right EHSI on the right DC circuit breaker plate of aircraft, right DPU, power transfer relay, right emergent bus-bar, mounting bracket.The power supply of left EADI, left EHSI, left DPU is connected directly to the emergent bus-bar in a described left side as shown in Figure 3, for the demonstration of crucial navigation information under emergency rating.The power supply of right EADI on right DC circuit breaker, right EHSI, right DPU is connected to the emergent bus-bar in the described right side by two and the power transfer relay that connects as shown in Figure 4; The excitatory end of power transfer relay is connected to normal bus-bar.The effect of relay mainly contains: when aircraft is under emergency service situation, the electric weight that a set of flying instruments in the right can battery consumption, has guaranteed enough emergent flying powers; Under supply regular power situation, when any one relay lost efficacy, right side flight instrument system can, because power down quits work, not eliminated the potential safety hazard that Single Point of Faliure brings to aircraft.
Claims (1)
1. an Electronic Flight Instrument electric power system, comprises the left electronic type attitude director indicator (EADI), left electron type level notch indicator (EHSI), left display processor (DPU), the left emergent bus-bar that are arranged on the left DC circuit breaker plate of aircraft; Be arranged on right electronic type attitude director indicator (EADI), right electron type level notch indicator (EHSI), right display processor (DPU), power transfer relay, right emergent bus-bar, mounting bracket on the right DC circuit breaker plate of aircraft, it is characterized in that: the power supply of the upper left electronic type attitude director indicator of described left DC circuit breaker (EADI), left electron type level notch indicator (EHSI), left display processor (DPU) is connected directly to the emergent bus-bar in a described left side; The power supply of the right electronic type attitude director indicator (EADI) on described right DC circuit breaker, right electron type level notch indicator (EHSI), right display processor (DPU) is connected to the emergent bus-bar in the described right side by described power transfer relay; Described power transfer relay is comprised of two relays of doing Anti-misplug design, and the excitatory end of described power transfer relay is connected with the normal bus-bar of major alarm reset circuit breaker in flight instrument system; Described power transfer relay is connected to avionics system electronic equipment rack by mounting bracket.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310577406.1A CN103587707B (en) | 2013-11-15 | 2013-11-15 | A kind of Electronic Flight Instrument electric power system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310577406.1A CN103587707B (en) | 2013-11-15 | 2013-11-15 | A kind of Electronic Flight Instrument electric power system |
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| CN103587707A true CN103587707A (en) | 2014-02-19 |
| CN103587707B CN103587707B (en) | 2015-08-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979706A (en) * | 2019-10-11 | 2020-04-10 | 中国直升机设计研究所 | Dual-voltage helicopter power supply system |
Citations (5)
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| CN201066769Y (en) * | 2007-08-02 | 2008-05-28 | 西安威胜航空科技发展有限公司 | Plane power management system |
| US20080211237A1 (en) * | 2006-11-23 | 2008-09-04 | Hispano Suiza | Electrical power supply for an aircraft |
| CN102520621A (en) * | 2011-11-22 | 2012-06-27 | 中国商用飞机有限责任公司 | Analog control board of aircraft power supply system |
| WO2012112090A1 (en) * | 2011-02-17 | 2012-08-23 | Saab Ab | Flight data display |
| CN202915931U (en) * | 2012-08-20 | 2013-05-01 | 中航华东光电有限公司 | Display of airplane emergency electronic backup instrument |
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2013
- 2013-11-15 CN CN201310577406.1A patent/CN103587707B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080211237A1 (en) * | 2006-11-23 | 2008-09-04 | Hispano Suiza | Electrical power supply for an aircraft |
| CN201066769Y (en) * | 2007-08-02 | 2008-05-28 | 西安威胜航空科技发展有限公司 | Plane power management system |
| WO2012112090A1 (en) * | 2011-02-17 | 2012-08-23 | Saab Ab | Flight data display |
| CN102520621A (en) * | 2011-11-22 | 2012-06-27 | 中国商用飞机有限责任公司 | Analog control board of aircraft power supply system |
| CN202915931U (en) * | 2012-08-20 | 2013-05-01 | 中航华东光电有限公司 | Display of airplane emergency electronic backup instrument |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979706A (en) * | 2019-10-11 | 2020-04-10 | 中国直升机设计研究所 | Dual-voltage helicopter power supply system |
| CN110979706B (en) * | 2019-10-11 | 2022-12-30 | 中国直升机设计研究所 | Dual-voltage helicopter power supply system |
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| CN103587707B (en) | 2015-08-05 |
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Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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Effective date of registration: 20210617 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |
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